US 12,234,741 B2
Thermal energy system to minimize or eliminate rotor bow
Govindaraj Kalyanasamy, Indianapolis, IN (US); and Peter Schenk, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on Apr. 20, 2023, as Appl. No. 18/304,037.
Prior Publication US 2024/0352872 A1, Oct. 24, 2024
Int. Cl. F01D 25/10 (2006.01); F01D 5/18 (2006.01); F01D 19/02 (2006.01); F02C 9/00 (2006.01)
CPC F01D 25/10 (2013.01) [F01D 5/18 (2013.01); F01D 19/02 (2013.01); F02C 9/00 (2013.01)] 16 Claims
OG exemplary drawing
 
15. A method comprising:
determining, by a controller, that operation of a gas turbine engine has concluded; and
responsive to determining that the operation concluded;
transporting electrical energy sourced from one or more batteries to one or more heaters via one or more electrical conductors which pass through an electrical transmission route through a hollow vane of the gas turbine engine, and
adding, via the one or more heaters, thermal energy to one or more portions of the gas turbine engine, wherein the thermal energy is configured to minimize or prevent undesired contact or seizing of a rotor with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation.